Wing mounted flaps



Feb. 11, 1947. 2,415,710- Q MING MOUNTED FLA? I I Filed June 10, 1942 '5Sheets-Sheet? Feb. 11,1947. RT 2,415,710

' WING MOUNTED FLAP Filed June 10, 1942 5 SheetsSl eet s H 11 mi??? Feb.11, 19 1f Q 2,415,710,

I WING MOUNTED FLAP Fil ed June 10, 1942 5 Sheet-Sheet 5 Patented Feb.11, 1947 nmrso stares rarest WKNG MGUNTED FLAPS Robert T. Smith,Eufaula, Okla.

Application June 10, 1942, Serial No. 446,500

1 Claim.

This invention relates to improvements in airplanes and moreparticularly to airplanes adapted to be used in warfare.

It is a primary object of the invention to provide means for increasingthe maneuverability of large airplanes and to enable such airplanes toascend more rapidly and at slower speed and to descend at slow speed tothus enable, large, heavily laden airplanes to use smaller air fields.

More particularly, it is an aim of the invention to provide a pluralityof pusher type propellers for use in conjunction with tractor typepropellers of airplanes, Which pusher type propellers are mounted to beswung to positions facing either upwardly or downwardly or forwardly orrearwardly of an airplane on which they are mounted to enable them tofunction to check the forward motion of the airplane, to increase itsforward motion, to force the airplane downwardly, or to force theairplane upwardly.

Still another object of the invention is to provide sets of flapscontrolled by common operating means from within the airplane and whichare adapted to be simultaneously opened for checking the forward motionof the airplane and for lifting the forward end thereof.

Still another object of the invention is to provide an airplane equippedwith. various types of guns mounted in the nose, the wing tips, thefuselage and the tail thereof.

Other objects and advantages of the invention will hereinafter becomemore fully apparent from the following description of the drawings,which illustrate a preferred embodiment thereof, and wherein:

Figure l is a top plan view of an airplane constructed in accordancewith the invention,

Figure 2 is an enlarged side elevational view, partly in section of thesame,

Figure 3 is a fragmentary longitudinal sectional View of a portion ofthe bottom of the airplane,

Figure 4 is a cross sectional view of said portion, taken substantiallyalong a plane as indicated by the line l4 of Figure 3,

Figure 5 is an enlarged longitudinal vertical sectional view takensubstantially along the plane of the line 55 of Figure 1,

Figure 6 is an enlarged horizontal sectional view of a portion of theairplane, taken substantiall along a plane as indicated by the line ofFigure Figure 7 is a fragmentary horizontal sectional view takensubstantially on the same horizontal plane as Figure 6,

Figure 8 is a vertical sectional view taken substantially along theplane of the line 3-8 of Figure 6,

Figure 9 is a similar View but showing the flap of Figure 8 in an openposition.

Figure 10 is an enlarged vertical sectional View taken substantiallyalong the plane of the line ld--lii of Figure 1, and

Figure 11 is a vertical sectional view taken substantially along theplane of the line ll-H of Figure 6.

Referring more particularly to the drawings, wherein like referencecharacters designate like or corresponding parts throughout thedifferent views, i2 designates generally an airplane constructed inaccordance with the invention, of the monoplane type, and which includesa fuselage, designated generally it, and a wing, designated generallyit. The fuselage it includes a cabin is having windows it and doors ll.

Disposed in the nose iii of the fuselage l3 and forwardly of the cabini5 is an upper gunners cockpit i9 and a lower machine gunners cockpit26. The cockpit is is provided with a rotatably mounted turret 2isupported for rotation on ball bearings 22 and having a top 23 of glassor other transparent material. lhe turret H is provided with a gun slot2 through which projects an anti-aircraft gun 25 which is mounted forswinging movement relatively to the slot 24. The front cockpit is alsopreferably contains a gun rack 26. Cockpits l9 and 2B are separated fromthe forward end of the cabin l5 by a wall or partition 27! and thecockpit 2%] is disposed beneath the cockpit l9 and is provided at itsforward end with a window 23 and in the sides thereof with portholes 2Qfor machine guns, not shown. The cock it it has a door 38 at each sidethereof opening outwardly of the fuselage and a trap door 3! whichconnects the cockpits i9 and 2B. The doors 3f: open outwardly ontocatwalks 32 and ladders 35 lead upwardly from said catwalks and onto thewing M. A compartment 3% is disposed in the fusela e l3 below the cabini i and the cockpit 2d and is like- Wise provided with a plurality ofports 29 in each side thereof in which machine guns are adapted to bepositioned. The compartment as connects with the cockpit ill by anopening 35 down from which leads a ladder 36. In the forward end of thecompartment 35 is mounted a cannon El which projects outwardly through aslot 38 and which is mounted for swinging movement relatively thereto.

Mounted in the leading edge of the wing ii are four motors 35, two ofwhich are positioned on each side of the fuselage l3. motors 39 isprovided, beyond its forward end, with a tractor type propeller it. Thetrailing edge of the wing it is provided with recesses M on each side ofthe fuselage 93. A shaft d2 extends longitudinally of the wing M andtransversely through the cabin l5 and longitudinally through the recessportions All. The shaft 42 is journaled in bearings 43, mounted in thewin Each of the l4, and in bearings 44, which are supported by the wingand which extends into the recesses 4|. The shaft 42 is provided withspaced clamps or attaching means 45 of any suitable construction, ineach of which is mounted a motor 46. The motors 46 are disposed directlybehind the motors 39 and are each provided with a pusher type propellerd! at one end thereof and a counterbalancing weight 48 at its oppositeend.

Referring particularly to Figure 7, a bevelled gear 49 is keyed to theportion of the shaft 42, which extends through the cabin l5, and mesheswith a bevelled gear 49 which. is keyed to one end of a shaft 50, whichis disposed within the cabin I and which is supported by and journaledin bearings 5| and 52, which are attached to a side wall of the cabinl5. A shaft 53 is journaled in an angular extension 5 of the bearing .5!and in a bearing 55 and is provided with a bevelled gear 56 which mesheswith a bevelled gear 51, keyed to the opposite end of the shaft 59. Theshaft 53 is provided with a hand wheel 58 which is adapted to bemanually turned for rotating the motor shaft 42, for a purpose whichwill hereinafter be described.

Referring particularly to Figures 1, 8 and 9, on

each side of the fuselage l 3 and in the upper part of the wing I4 ismounted a flap 59. The flaps 59 are disposed longitudinally of the wing14 and are normally nested in recesses 69 in the upper side thereof. Apair of rods 6i extend upwardly from each of the recesses 6!! and theflaps 59 are provided with openings 62, adjacent their trailing edges,for loosely engaging the rods 6!.

A pair of arms 63 are attached to the upper side of each of the flaps 59and project beyond the leading edge thereof and to beyond the leadingedge of the wing M. A shaft 64 extends transversely through the fuselagel3 and is disposed beneath and longitudinally of the wing I4 and isjournaled in brackets 65 which depend from the wing. A plurality ofcrank arms 66 are keyed 'to and project forwardly from the shaft 64.Each of the crank arms 65 is connected at its forward end to the forwardend of an arm 63 by means of a link 6'! which is pivotally connected tosaid arms 63 and 66.

Beyond the flaps 59, the wing 14 is provided with recesses 68 in itsupper side in which are adapted to be nested flaps as. The flaps 69 arepivotally mounted in the wing Hi at their leading 'edges by rods orshafts la. The wing is is provided with openings H which extend there-"M which depend from the wing. Each shaft 73 is provided with one or aplurality of crank arms i5 which project downwardly and forwardlytherefrom and tothe free end of which is pivotal ly connected the lowerend of one of the links 72. 'The' shafts 73 are also provided withdepending crank arms I6 to the lower ends of which are pivotallyconnected the rear ends of links 71.

The shaftsd has depending crank arms 78 keyed thereto and to the lowerends of which are pivotally connected the forward ends of the links H,for a, purpose which will hereinafter be de-.

scribed. v

A shaft 19 extends transversely through the cockpit l9 and is journaledin the sides of the fuselage I3, as best seen in Figure 6. The ends ofthe shaft 19 project outwardly from the fuselage 13 and have flaps 88fixedly connected thereto and projecting forwardly therefrom. As seen inFigure 6, the shaft 64 extends transversely through the forward part ofthe cabin l5 and the portion thereof which is disposed in the cabin hascrank arms 8| and 82 keyed thereto and projecting upwardly therefrom.The flaps 86 are provided, adjacent their forward ends and inner edges,with upwardly projecting eye screws 83 to each of which is pivotallyconnected an end of a link 84. The links 84 extend rearwardly throughslots 85 in the sides of the fuselage l3 and through slots 86 in thewall 21 and one of said links is pivotally connected at its opposite endto the free end of the crank arm 8| and the other of said links ispivotally connected at its rear end to the free end of the crank arm 82.

A flap 87 is mounted on the trailing edge portion of the wing M,adjacent to and at each side of the fuselage 13. As best seen in Figure11, the trailing edge of the wing I4 is provided with upwardlyprojecting hook-shaped members 88 and the trailing edges of the flap 8'!are provided with eyes 89 for slidably engaging the shanks of themembers 88. A shaft 96 extends transversely through the cabin l5 and isjournaled in the sides of the fuselage [3. The ends of the shaft 90 aredisposed beneath the flap 8'! and are provided with crank arms 9| toeach of which is pivotally connected a link 92. Links 92 extend upwardlythrough openings 93 in the wing M and are pivotally connected at theiropposite ends to the flaps 8?, near their leading edges.

As best seen in Figure 6, a crank arm 94 is keyed to the shaft 90 andprojects downwardly therefrom and is disposed in the cabin I5. A link 95is pivotally connected at its forward end to the crank arm 82 and at itsrear end to the crank arm 94. A lever 5'6 is keyed t0 the shaft 64 andis disposed within the cabin I5 and is adapted to be manually operatedfor turning the shaft 64. When the shaft 64 is thus turned in aclockwise direction, as seen in Figures 2 and 10, the crank arms 65 willbe swung upwardly to raise the flaps 59 to the position, as seen in Figure 9. Likewise, the cranks 18 will be swung forwardly to swing thecranks I6 forwardly, so as to swing the crank arms 15 upwardly to raisethe flaps 59 to their dotted line positions of Figure 10. The sameturning movement of the shaft 6t will also rock the crank arms 8! and 82rearwardly to raise the forward ends of the flaps 80 and will turn theshaft 96 in the opposite direction, through the link connection 95 forraising the forward end of the flap 81. It will be readily apparent thatthe flaps 59, 80 and 87, when thus elevated, will tend to check theforward speed of the airplane l2 and to lift the nose thereof forpulling the airplane out of a nose dive or for checking its forwardmomentum to enable it to land at a slower speed. By returning the lever96 to its original position, the flaps will all be returned to theirnested positions and the flaps $9 will function to assist in turning theshafts 64 in a counterclockwise direction as the pressure of the wind onthe upper sides thereof tends to force the flaps 68 back to nestedpositions.

Gun emplacements 9? are mounted on the upper sides of the tips of thewing I4 and on the tail 98 of the airplane l2 and include doors 99,windows [U9 and machine gun ports I61. Also,

from each of the gun emplacements 91 projects a cannon IE2.

Referring particularly to Figs. 1 and 2, the fuselage I3 is provided inits upper part and behind the cabin It with an aircraft gunners cockpitIE3 containing one or more aircraft guns sec and which is adapted to beclosed by means of a sliding hatch I 35 which is mounted on suitableball bearings. Rearwardly of the cockpit B3 are catwalks I85 upwardlyfrom which lead ladders I81 which afford access to the cockpit I63.

Beneath the cockpit I213 is a compartment I113, as seen in Figure 2, inwhich is mounted a storage battery Its, an air pump I III, an airstorage tank I II and a gas storage tank I12, which parts may be of anysuitable construction. An air inlet pipe I13 having a check valve I I Iis connected to one side of the pump I It and a conduit I i5, providedwith a shut-off valve, connects the other side of the pump to the tank II I. The tanks II I and I I2 are connected by a conduit I It and aconduit I I1 leads from the tank I12. The conduits I16 and III arelikewise provided with suitable shut-off valves, as seen in Figure 2.The conduit I I1 leads along the underside of the rear portion of thefuselage I3 and connects with gas guns I I8 which project from the rearend of the airplane. Branch conduits H9 are also connected to the tank II2 or its conduit I H, at any suitable point, now shown, and have endswhich open beneath the cannon H32. Electric conductors I251 lead fromthe storage battery I39 to the outlet of each of the branch pipes I I9,so that when the tank I I2 contains an inflammable gas, the gas can beignited by a spark from the conductors I21! so that the cannons 31 andH12 and the guns H8 can be utilized as flame throwers.

Beneath the fuselage I3 between the forward ground wheels of theairplane I2 is located a torpedo or bomb rack I21 which may be of anysuitable construction. The bomb rack I2I, as best seen in Figures 3 and4, is illustrated as being provided with an open forward end I22,adapted to be normally closed by means of a lever-operated valve orshutter I23 which can be operated from within the compartment 33, andpreferably includes a trap door I25 which opens into the compartment3 1. Suitable means, not shown, may be provided for projecting a bomb ortorpedo, not shown, outwardly through the open forward end I22 when thevalve or shutter I23 is in an open position.

Referring back to the motors 6, as seen in Figures 1 and 2, the bladesof the propellers ll thereof are pitched in the opposite direction tothe blades of the propellers so so that when the propellers 41 are beingdriven and are in the positions, as seen in Figures 1 and 2, thetendency Will be to drive the airplane I2 rearwardly so as to check theforward motion thereof and to act against the action of the propellers43. By turning the hand wheel 58 in one direction the shaft 42 will beturned for moving the motors 43 and propellers 31 from their positionsin Figures 1 and 2 to positions in which the propellers 41 are insubstantially horizontal planes and beneath the wing It, and when thusdisposed the propellers 47 will function efiiciently for lifting theairplane I2 to thereby enable it to ascend much more rapidly and whilemoving at a much slower forward 7 speed than would be possible for theairplane to otherwise ascend by the use of the propellers ill only.Also, the airplane I2 could be assisted in ascending by opening theflaps and their tendency to check the forward motion of the airplanewill not create any risk of the motors 33 stalling, resulting in a tailspin, due to the fact that substantially all of the weight of theairplane I2 will be supported by the power exerted by the propellers d1.Also, by turning the shaft t2 in the opposite direction, by operation ofthe hand wheel 58, the propellers M can be moved from their positions ofFigures 1 and 2 to positions in horizontal planes above the wing It sothat the propellers ll will then act to force the airplane downwardly.In addition, the shaft 42 can be turned to swing the motors 46 throughan arc of one hundred and eighty degrees from their positions of Figures1 and 2 so that the propellers 41 will then be facing to the rear, inwhich position they will function as pusher type propellers to assistthe propellers M in driving the airplane I2 in a forward direction.Obviously, suitable means, not shown, may be provided for controllingthe motors it so that they can be operated only when needed.

Various modifications and changes are contemplated and may obviously beresorted to, provided they fall within the spirit and scope of theinvention as hereinafter defined by the appended claim, as only apreferred embodiment of the invention has been disclosed.

I claim as my invention:

An aircraft having flaps mounted in a wing thereof, said wing havingrecesses in its upper side for receiving the flaps, rods projectingupwardly from the wing and through the trailing edge portion of certainof the flaps, said portions being slidably mounted on the rods, a shaftjournaled beneath the wing, and link and lever means for connecting theshaft to the leading edges of said last mentioned flaps whereby theflaps will be raised when the shaft is turned in one direction, andlowered when the shaft is turned in the opposite direction other of theflaps being pivotally connected to the wing at their leading edges, andlink and lever means actuated by the shaft for raising and lowering thepivoted flaps simultaneously with the aforementioned flaps, said pivotedfiaps functioning to urge said other flaps toward nested positionsROBERT T. SMITH.

REFERENCES CITED The following references are of record in the file ofthis patent:

UNITED STATES PATENTS Number Name Date 1,916,813 Sessa July 4, 1933 01,862,421 OMalley June 7, 1932 2,005,965 Barnhart June 25, 19352,041,688 Barnhart May 26, 1936 2,049,188 Alfaro July 28, 1936 1,758,355Cottrell et a1 May 13, 1930 65 1,752,012 Lauchin Mar. 25, 1930 1,805,770Kelly May 19, 1931 1,935,824 Upson Nov. 21, 1933 FOREIGN PATENTS 0Number Country Date 332,145 German Jan. 24, 1921

